CN107054637B - Folding system of multi-rotor helicopter - Google Patents
Folding system of multi-rotor helicopter Download PDFInfo
- Publication number
- CN107054637B CN107054637B CN201710380988.2A CN201710380988A CN107054637B CN 107054637 B CN107054637 B CN 107054637B CN 201710380988 A CN201710380988 A CN 201710380988A CN 107054637 B CN107054637 B CN 107054637B
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- CN
- China
- Prior art keywords
- rotor
- folding
- cantilever
- worm wheel
- seat
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
- B64C1/063—Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/50—Blades foldable to facilitate stowage of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The utility model relates to the technical field of helicopter manufacturing, in particular to a multi-rotor helicopter folding system. The utility model can provide a multi-rotor helicopter folding system, which improves the reliability of folding and unfolding of a helicopter wing by combining a structure provided with a worm gear, a control unit and a relay. The utility model provides a multi-rotor helicopter folding system, which comprises a folding device with a three-rotor, four-rotor or six-rotor structure. The utility model has wide application, such as military, civil, agricultural, commercial, unmanned aerial vehicle, model airplane, etc.
Description
Technical Field
The utility model relates to the technical field of aircraft manufacturing, in particular to a multi-rotor helicopter folding system.
Background
The vertical take-off and landing aircrafts in the market at present mainly comprise an electric multi-rotor, a direct-drive multi-rotor, a single-rotor helicopter, a coaxial double-rotor helicopter and the like.
Chinese patent CN201385780Y discloses a propeller on an aircraft, in particular to a novel foldable and telescopic propeller, which comprises a rotating shaft and paddles mounted on the rotating shaft, and is characterized in that the end of the main paddle is provided with a chute, the root of the telescopic paddle is provided with a secondary chute, the telescopic paddle is sleeved in the chute at the end of the main paddle, the main paddle is sleeved in the secondary chute of the telescopic paddle, and the main paddle is connected with a hinge chain of the rotating shaft. The telescopic blade is arranged on the main blade, so that the change of the rotation diameter of the blade can be realized, the thrust of an airplane is effectively changed, and the telescopic blade is particularly suitable for being used on an automobile aircraft and has the characteristic of simple structure.
The above patent also has an unreasonable structure, and cannot ensure that the wing can be smoothly opened and retracted each time.
Disclosure of Invention
The technical problem to be solved by the utility model is to provide a multi-rotor helicopter folding system, which improves the reliability of folding and unfolding of the helicopter wings by combining a worm gear structure, a control unit and a relay.
In order to solve the problems, the folding system of the multi-rotor helicopter provided by the utility model comprises a folding device, wherein the folding device comprises cantilever fixing seats which are controlled by a control unit and are respectively arranged on a bracket, a cantilever is arranged in a middle hole formed by mutually buckling the cantilever fixing seats and the cantilever locating seats, pin holes are formed in the cantilever fixing seats and the cantilever locating seats, a cantilever folding seat is arranged at one end of each cantilever, two folding reference shafts are oppositely arranged at the outer sides of the cantilever folding seats, a folding worm wheel is arranged at one side of each folding reference shaft, a first travel limit sensor is arranged at the bottom of each folding worm wheel, the folding worm wheel is meshed with a folding driving worm arranged at the outer sides of the folding worm wheel to be transmitted, a folding assembly is arranged in each cantilever folding seat and is connected with a cantilever seat assembly, a transmission shaft folding assembly is arranged on each cantilever seat assembly, and the transmission shaft folding assembly is connected with a rotor wing correction worm wheel provided with a transmission assembly fixing seat;
the locking pin arranged on the transmission assembly fixing seat is connected with a locking pin driving worm gear through a spring, the locking pin driving worm gear is connected with the locking pin and a rotor wing position correcting driving worm, and third stroke limit sensors are arranged on the locking pin and the rotor wing position correcting driving worm;
the other end of the cantilever is provided with a transmission shaft and a rotor wing, the transmission shaft is connected with a rotor wing correcting worm gear, the transmission shaft is movably connected with the end part of the rotor wing correcting worm gear through a folding reference shaft, and the shaft end of the rotor wing correcting worm gear is a transmission shaft driving end;
the end part of the rotor wing is provided with a rotor wing driving worm wheel, and the rotor wing driving worm wheel is meshed with a rotor wing driving worm arranged on a rotor wing driving motor for power transmission;
the cantilever folding seat is arranged at the end part of the rotor shaft, and the rotor shaft is provided with a rotor shaft flange, a variable-pitch seat, a connecting rod seat and a sphere from top to bottom in sequence;
the control unit and the relay are respectively electrically connected with the first stroke limit sensor, the second stroke limit sensor, the third stroke limit sensor, the fourth stroke limit sensor, the folding driving worm motor, the locking pin and the rotor wing position correcting driving worm motor and the rotor wing folding driving motor for signal transmission.
The preferred technical scheme, the rotor is equipped with the arc to its inside shrink with rotor drive worm wheel's hookup location.
According to the preferable technical scheme, any one end of the locking pin is a threaded end, and the threaded end is connected with the worm wheel connecting end of the rectangular structure.
The preferred technical scheme comprises a three-rotor, four-rotor or six-rotor device which is controlled by a control unit and is arranged on a bracket.
The preferable technical scheme is that the three-rotor wing device comprises a folding device which is arranged on a triangular bracket and is 120 degrees.
The preferable technical scheme is that the four-rotor wing device comprises a folding device which is arranged on a round bracket and is arranged at 45 degrees.
Preferably, the six-rotor device comprises a folding device which is arranged on a circular bracket and is arranged at an angle of 60 degrees.
The preferable technical scheme is that motors of a driving worm motor, a locking pin, a rotor wing correcting driving worm and a rotor wing driving motor are all connected in series, wherein a group of motors are used as standby motors.
According to the preferable technical scheme, the rotation axis of the rotor wing is the axis of the worm wheel and is folded towards the cantilever direction of the machine body.
Compared with the prior art, the multi-rotor helicopter folding system provided by the utility model has the following beneficial effects:
1. the utility model has wide application, and can be applied to various fields such as military, civil, agricultural, commercial, unmanned aerial vehicle, model airplane and the like.
2. The wing folding device is simple in structure and can smoothly open and fold the wing.
Drawings
Figure 1 is a top view of a three rotor of the multi-rotor helicopter folding system of the utility model;
figure 2 is a top view of a quad-rotor of the multi-rotor helicopter folding system of the utility model;
figure 3 is a top view of a six rotor of the multi-rotor helicopter folding system of the present utility model;
FIG. 4 is a perspective view of a multi-rotor helicopter folding system according to the utility model;
figure 5 is an internal block diagram of the multi-rotor helicopter folding system of the utility model;
figure 6 is a front view of the internal structure of the multi-rotor helicopter folding system of the present utility model;
figure 7 is a top view of the multi-rotor helicopter folding system of the utility model;
figure 8 is an interior front view of the multi-rotor helicopter folding system of the utility model;
figure 9 is a top view of the internal structure of the multi-rotor helicopter folding system of the present utility model;
figure 10 is a perspective view of a folding boom mount in a multi-rotor helicopter folding system according to the utility model;
FIG. 11 is a perspective view of the locking pin of the multi-rotor helicopter folding system of the utility model;
FIG. 12 is a perspective view of the drive shaft of the multi-rotor helicopter folding system of the utility model coupled to a rotor positioning worm gear;
fig. 13 is a front view of fig. 12;
figure 14 is a front view of a rotor in the multi-rotor helicopter folding system of the utility model;
figure 15 is a front view of a boom in a multi-rotor helicopter folding system according to the utility model;
figure 16 is a front view of the boom and rotor of the multi-rotor helicopter folding system of the utility model;
FIG. 17 is an internal block diagram of a middle rotor of the multi-rotor helicopter folding system of the utility model;
figure 18 is a position set-up view of a fourth travel switch of the multi-rotor helicopter folding system of the utility model;
FIG. 19 is a block diagram of a wing drive worm and worm gear in a multi-rotor helicopter folding system according to the utility model;
FIG. 20 is a diagram of the rotary shaft connection in the multi-rotor helicopter folding system of the present utility model;
figure 21 is a schematic diagram of the operation of the control unit in the multi-rotor helicopter folding system according to the utility model.
Reference numerals
In the figure: the device comprises a cantilever, a 2-locking pin, a 3-folding turbine, a 4-folding driving worm, a 5-transmission component fixing seat, a 6-spring, a 7-locking pin driving turbine, an 8-rotor positioning driving worm, a 9-fourth stroke limit sensor, a 10-rotor positioning worm wheel, a 11-third stroke limit sensor, a 12-second stroke limit sensor, a 13-folding reference shaft, a 14-radial arm folding seat, a 15-transmission shaft, a 16-driving end, a 17-first stroke limit sensor, a 18-radial arm fixing seat, a 19-pin hole, a 20-radial arm positioning seat, a 21-thread end and a 22-worm wheel connecting end; 30-rotor, 31-folding assembly, 32-rotor driving worm, 33-rotor driving worm wheel, 34-rotor driving motor, 35-transmission shaft folding assembly, 36-radial arm seat assembly, 37-variable-pitch seat, 38-sphere, 39-connecting rod seat, 40-rotor shaft flange and 41-rotor shaft.
Detailed Description
Hereinafter, embodiments of the present utility model will be described in detail with reference to the accompanying drawings.
Example 1
As shown in fig. 1, 4 to 21, the present embodiment provides a multi-rotor helicopter folding system, which is a three-rotor folding system, and the specific structure is described in detail by taking the structure in the three rotors as a representative, and the folding device of the specific structure includes a cantilever fixing seat 18 controlled by a control unit and respectively arranged on a triangular bracket, a cantilever 1 is arranged in a middle hole formed by mutually buckling the cantilever fixing seat 18 and a cantilever positioning seat 20, pin holes 19 are arranged on the cantilever fixing seat 18 and the cantilever positioning seat 20, one end of the cantilever 1 is provided with a cantilever folding seat 14, two folding reference shafts 13 are oppositely arranged on the outer sides of the cantilever folding seat 14, one side of the folding reference shaft 13 is provided with a folding worm wheel 3, the bottom of the folding worm wheel 3 is provided with a first travel limit sensor 17, the folding worm wheel 3 is meshed with a folding driving worm 4 arranged on the outer sides of the folding worm wheel, a folding assembly 31 is arranged in the cantilever folding seat 14, the folding assembly 31 is connected with a cantilever seat assembly 36, a transmission shaft assembly 35 is arranged on the cantilever seat assembly 36, and the transmission shaft folding assembly 35 is connected with a rotor 10 provided with the calibration seat 5;
the locking pin 2 arranged on the transmission assembly fixing seat 5 is connected with the locking pin driving worm wheel 7 through a spring 6, the locking pin driving worm wheel 7 is connected with the locking pin and the rotor wing position correcting driving worm 8, and a third stroke limit sensor 11 is arranged on the locking pin and the rotor wing position correcting driving worm 8;
the other end of the cantilever 1 is provided with a transmission shaft 15 and a rotor wing 30, the transmission shaft 15 is connected with a rotor wing correcting worm wheel 10, the transmission shaft 15 is movably connected with the end part of the rotor wing correcting worm wheel 10 through a folding reference shaft 13, and the shaft end of the rotor wing correcting worm wheel 10 is a transmission shaft driving end 16;
a rotor driving worm wheel 33 is arranged at the end part of the rotor 30, and the rotor driving worm wheel 33 is meshed with a rotor driving worm 32 arranged on a rotor driving motor 34 for power transmission; as shown in fig. 18 and 19, in this embodiment, the rotation axis of the rotor 30 is a worm wheel axis and is folded toward the fuselage cantilever 1. The cantilever folding seat 14 is arranged at the end part of the rotor shaft 41, and the rotor shaft 41 is provided with a rotor shaft flange 40, a variable-pitch seat 37, a connecting rod seat 39 and a sphere 38 from top to bottom in sequence;
the control unit and the relay are respectively electrically connected with the first stroke limit sensor 17, the second stroke limit sensor 12, the third stroke limit sensor 11, the fourth stroke limit sensor 9, the folding driving worm motor, the locking pin, the rotor wing position correcting driving worm motor and the rotor wing folding driving motor for signal transmission, and the connection position of the rotor wing 30 and the rotor wing driving worm gear 33 is provided with an arc shape shrinking towards the inside. Wherein, any end of the locking pin 2 is a threaded end 21, and the threaded end 21 is connected with a worm wheel connecting end 22 with a rectangular structure.
The utility model provides a multi-rotor helicopter folding system, which has the following working principle: according to the utility model, a folding electric signal provided by a control unit is used for starting a locking pin and a rotor position correcting driving motor to drive a rotor fixing seat for withdrawing the locking pin 2, a threaded end 21 is arranged on the locking pin 2, the threaded end 21 automatically stops reciprocating motion when the locking pin 2 moves to the tail position, a second stroke limit sensor 12 sends a locking pin 2 position signal to a relay, a relay group is used for providing an electric signal to start a third stroke limit sensor 11, meanwhile, the locking pin and the rotor position correcting driving motor 8 continuously work to drive a rotor position worm wheel 10 to enable a propeller and a propeller clamp to move to a position perpendicular to a cantilever 1, at the moment, a folding reference shaft 13 on a folding assembly 31 and a folding reference shaft 13 on a rotor arm seat are concentric or nearly concentric, the third stroke limit sensor 11 transmits detected rotor position information of the rotor position worm wheel 10 to the relay, the relay starts a folding driving worm motor and a rotor driving motor 34 through the signal, and when the cantilever 1 and the rotor are folded to a target position, and the first stroke limit sensor 17 and the fourth stroke limit sensor 9 send the folding position information of the worm wheel 3 to the relay group through the single-chip microcomputer to be closed. The distance-changing seat 37 and the connecting rod seat 39 are internally provided with power supply electric contacts of the rotor driving motor 34 and the fourth stroke limit sensor 9, the power supply contacts in the connecting rod seat 39 are designed to be distributed in the A or B direction, and the power supply contacts in the distance-changing seat 37 are designed to be distributed in the A, B direction; rotor folding drive motor 34 is exemplified by a brush motor: the power contacts in the A, B direction distributed in the torque converter 37 are designed to be opposite in polarity to the power contacts in the link mount 39 to ensure that the rotor folding direction is the rotor 30 direction, regardless of whether the rotor set a or B direction is facing the rotor 30. The control unit gives out an electric signal to start the locking pin and the rotor wing correcting driving motor and gives out an electric signal to control the steering engine to push the connecting rod seat 39 upwards to enable the distance changing seat 37 to be in contact with the rotor wing shaft flange 40, so that the distance changing seat 37 and the power contacts in the connecting rod seat 39 are in a contact position, and when the folding reference shaft 13 on the folding assembly 31 is concentric or nearly concentric with the folding reference shaft 13 on the radial arm folding seat 14, a group of power contacts of the distance changing seat 37 are in contact with the power supply contacts on the distance changing seat 37; when the folding driving worm motor is started, the rotor folding motor is started to drive the rotor 30 to fold. The rotor wing correcting worm wheel 10 of the locking pin 2 and the assembling position of the locking pin 2 are designed with holes corresponding to the locking pin 2, and the rotor wing correcting worm wheel 10 is designed not to axially move with the locking pin 2 and only rotates;
a spring 6 is designed between the locking pin 2 and the rotor positioning worm wheel 10, the locking pin 2 passes through the transmission assembly fixing seat 5, threads corresponding to the threaded end 21 on the locking pin 2 are designed at the corresponding position of the transmission assembly fixing seat 5, a one-way bearing is designed at the installation position of the rotor positioning worm wheel 10 and the folding assembly 31, and the transmission shaft folding assembly 35 is not driven when the locking pin and the rotor positioning driving motor rotate reversely;
the use of identical or equivalent designs for the drive shaft folding assembly 35 is considered to be within the scope of this patent. The drive shaft folding assembly 35 is designed and mounted to be concentric with the radial arm folding seat 14. When the control unit expands the electric signal, the relay group starts the folding worm motor to reversely rotate and expand the spiral arm, when the rotor 30 expands to the target position, the relay starts the rotor folding driving motor 34 to reversely rotate and expand the rotor 30 through the feedback signal of the first stroke limiting sensor 17, when the rotor rotates to the target position, the relay group or the singlechip starts the locking pin and the rotor position correcting driving motor 8 to reversely rotate through the feedback signal of the fourth stroke limiting sensor 9, and the spring 6 between the locking pin and the rotor position correcting worm wheel 7 enables the locking pin 2 to be meshed with the corresponding threads 6 in the transmission assembly fixing seat 5, and the worm wheel 7 is driven to rotate through the locking pin so as to lock the cantilever 1. In this embodiment, the motor for folding the driving worm, the locking pin 2, and the rotor positioning driving worm, and the rotor driving motor 34 are preferably connected in series, in which one set of motors is used as a standby motor.
Example 2
This embodiment is modified on the basis of embodiment 1, and the other structures are the same, except that: as shown in fig. 2, the quadrotor device according to this embodiment includes a folding device disposed at 45 ° on a circular support.
Example 3
This embodiment is modified on the basis of embodiment 1, and the other structures are the same, except that: as shown in fig. 3, the six-rotor device comprises a folding device which is arranged on a circular bracket and is arranged at 60 degrees, and the rotors are arranged in an upper-lower layering way.
While the preferred embodiments and examples of the present utility model have been described in detail with reference to the accompanying drawings, the present utility model is not limited to the above-described embodiments and examples, and various changes may be made within the knowledge of those skilled in the art without departing from the spirit of the present utility model.
Claims (9)
1. The folding system of the multi-rotor helicopter is characterized by comprising cantilever fixing seats (18) which are controlled by a control unit and are respectively arranged on a support, wherein a cantilever (1) is arranged in a middle hole formed by mutually buckling the cantilever fixing seats (18) and the cantilever locating seats (20), pin holes (19) are formed in the cantilever fixing seats (18) and the cantilever locating seats (20), one end of each cantilever (1) is provided with a cantilever folding seat (14), two folding reference shafts (13) are oppositely arranged on the outer sides of the cantilever folding seats (14), one side of each folding reference shaft (13) is provided with a folding worm wheel (3), the bottom of each folding worm wheel (3) is provided with a first stroke limiting sensor (17), each folding worm wheel (3) is in meshed transmission with a folding driving worm (4) arranged on the outer sides of each folding worm wheel, a folding assembly (31) is arranged in each cantilever folding seat (14), each folding assembly (31) is connected with each cantilever seat assembly (36), each cantilever seat assembly (36) is provided with a transmission shaft assembly (35), and each transmission shaft assembly (35) is connected with a rotor wing (10) arranged on the corresponding fixing seat (5);
the locking pin (2) arranged on the transmission assembly fixing seat (5) is connected with the locking pin driving worm wheel (7) through a spring (6), the locking pin driving worm wheel (7) is connected with the locking pin and the rotor wing position correcting driving worm (8), and a third stroke limit sensor (11) is arranged on the locking pin and the rotor wing position correcting driving worm (8);
the other end of the cantilever (1) is provided with a transmission shaft (15) and a rotor wing (30), the transmission shaft (15) is connected with a rotor wing correcting worm wheel (10), the transmission shaft (15) is movably connected with the end part of the rotor wing correcting worm wheel (10) through a folding reference shaft (13), and the shaft end of the rotor wing correcting worm wheel (10) is a transmission shaft driving end (16);
the end part of the rotor (30) is provided with a rotor driving worm wheel (33), and the rotor driving worm wheel (33) is meshed with a rotor driving worm (32) arranged on a rotor driving motor (34) for power transmission;
the cantilever folding seat (14) is arranged at the end part of the rotor shaft (41), and the rotor shaft (41) is provided with a rotor shaft flange (40), a variable-pitch seat (37), a connecting rod seat (39) and a sphere (38) in sequence from top to bottom;
the control unit and the relay are respectively electrically connected with the first stroke limit sensor (17), the second stroke limit sensor (12), the third stroke limit sensor (11), the fourth stroke limit sensor (9), the folding driving worm motor, the locking pin, the rotor wing position correcting driving worm motor and the rotor wing folding driving motor for signal transmission.
2. A multi-rotor helicopter folding system according to claim 1 wherein the connection location of said rotor (30) to the rotor drive worm gear (33) is provided with an arc which is retracted inwardly thereof.
3. Multi-rotor helicopter folding system according to claim 1 characterized in that either end of said locking pin (2) is a threaded end (21), said threaded end (21) being connected with a worm gear connection end (22) of rectangular configuration.
4. The multi-rotor helicopter folding system of claim 1 wherein the multi-rotor helicopter folding system comprises a three-rotor, four-rotor or six-rotor device controlled by a control unit and disposed on a stand.
5. The multi-rotor helicopter folding system according to claim 4 wherein said tri-rotor assembly comprises a 120 ° arrangement of folding assemblies disposed on a delta-shaped stand.
6. The multi-rotor helicopter folding system according to claim 4 wherein said quad-rotor assembly comprises a 45 ° arrangement of folding devices disposed on a circular stand.
7. The multi-rotor helicopter folding system according to claim 4 wherein said six-rotor device comprises a folding device disposed at 60 ° on a circular stand.
8. A multi-rotor helicopter folding system according to claim 1 characterized in that the drive worm motor for folding, the locking pin (2) and the motor of the rotor positioning drive worm and the rotor drive motor (34) are all connected in series with a double motor, wherein one set of motors serves as a back-up motor.
9. The multi-rotor helicopter folding system according to claim 1 wherein the rotational axis of said rotor (30) is a worm gear axis and folds in the direction of the fuselage boom (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710380988.2A CN107054637B (en) | 2017-05-25 | 2017-05-25 | Folding system of multi-rotor helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710380988.2A CN107054637B (en) | 2017-05-25 | 2017-05-25 | Folding system of multi-rotor helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107054637A CN107054637A (en) | 2017-08-18 |
| CN107054637B true CN107054637B (en) | 2023-08-15 |
Family
ID=59609965
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710380988.2A Withdrawn - After Issue CN107054637B (en) | 2017-05-25 | 2017-05-25 | Folding system of multi-rotor helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107054637B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111806680B (en) * | 2020-06-19 | 2023-09-12 | 中国科学院地理科学与资源研究所 | Unmanned aerial vehicle flies away device and unmanned aerial vehicle |
| CN113879513B (en) * | 2020-07-02 | 2024-06-11 | 海鹰航空通用装备有限责任公司 | Automatic twist reverse folding oar clamp and have its screw |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1375658A (en) * | 1971-06-01 | 1974-11-27 | Textron Inc | |
| FR2836889A1 (en) * | 2002-03-11 | 2003-09-12 | Eurocopter France | Method of folding and unfolding of helicopter rotor blades involves locking one blade in position and moving other by linear actuator |
| CN101391651A (en) * | 2008-11-17 | 2009-03-25 | 西安智澜科技发展有限公司 | Foldable Y shaped three axis two-layer six rotorcraft |
| CN101575004A (en) * | 2009-06-09 | 2009-11-11 | 徐锦法 | Flight-mode-variable unmanned aircraft with multiple sets of coaxial rotors |
| US7857590B1 (en) * | 2006-08-11 | 2010-12-28 | Neal Larry R | Folding rotor for a rotorcraft |
| FR2991292A1 (en) * | 2012-06-04 | 2013-12-06 | Etienne Jean Rampal | Device for allowing retraction of blades around pin of single fastener on rotor of rotorcraft, has articulation arm whose end is pierced with hole fitted to leg fixed on blade root to transmit swing drive effort for retraction around pin |
| CN103723272A (en) * | 2014-01-05 | 2014-04-16 | 曹乃承 | Aircraft and transformation method for structural morphology of aircraft in flight |
| CN104590556A (en) * | 2014-10-31 | 2015-05-06 | 湖北易瓦特科技有限公司 | Foldable unmanned aerial vehicle |
| CN205087140U (en) * | 2015-11-04 | 2016-03-16 | 中航维拓（北京）科技有限责任公司 | Oil moves six coaxial rotor unmanned aerial vehicle frame systems of displacement |
| JP3207604U (en) * | 2016-09-09 | 2016-11-17 | 保瀚數位行銷有限公司 | Folding wing toy helicopter |
| CN206856987U (en) * | 2017-05-25 | 2018-01-09 | 桂艳春 | A kind of multirotor helicopter folding system |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9573683B2 (en) * | 2014-04-28 | 2017-02-21 | Arch-Aerial, Llc | Collapsible multi-rotor UAV |
| EP3297910B1 (en) * | 2015-05-19 | 2020-01-08 | Alion Science and Technology Corp. | Helicopter blade folding apparatus |
-
2017
- 2017-05-25 CN CN201710380988.2A patent/CN107054637B/en not_active Withdrawn - After Issue
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1375658A (en) * | 1971-06-01 | 1974-11-27 | Textron Inc | |
| FR2836889A1 (en) * | 2002-03-11 | 2003-09-12 | Eurocopter France | Method of folding and unfolding of helicopter rotor blades involves locking one blade in position and moving other by linear actuator |
| US7857590B1 (en) * | 2006-08-11 | 2010-12-28 | Neal Larry R | Folding rotor for a rotorcraft |
| CN101391651A (en) * | 2008-11-17 | 2009-03-25 | 西安智澜科技发展有限公司 | Foldable Y shaped three axis two-layer six rotorcraft |
| CN101575004A (en) * | 2009-06-09 | 2009-11-11 | 徐锦法 | Flight-mode-variable unmanned aircraft with multiple sets of coaxial rotors |
| FR2991292A1 (en) * | 2012-06-04 | 2013-12-06 | Etienne Jean Rampal | Device for allowing retraction of blades around pin of single fastener on rotor of rotorcraft, has articulation arm whose end is pierced with hole fitted to leg fixed on blade root to transmit swing drive effort for retraction around pin |
| CN103723272A (en) * | 2014-01-05 | 2014-04-16 | 曹乃承 | Aircraft and transformation method for structural morphology of aircraft in flight |
| CN104590556A (en) * | 2014-10-31 | 2015-05-06 | 湖北易瓦特科技有限公司 | Foldable unmanned aerial vehicle |
| CN205087140U (en) * | 2015-11-04 | 2016-03-16 | 中航维拓（北京）科技有限责任公司 | Oil moves six coaxial rotor unmanned aerial vehicle frame systems of displacement |
| JP3207604U (en) * | 2016-09-09 | 2016-11-17 | 保瀚數位行銷有限公司 | Folding wing toy helicopter |
| CN206856987U (en) * | 2017-05-25 | 2018-01-09 | 桂艳春 | A kind of multirotor helicopter folding system |
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